Airplane



y 1341- s. H, MOURNING ETAL 2.249.026

'DAIRPLANE Filed Feb. 28, 19:58 e Sheets-Sheet 1 Q INVENTOS agzmxm ATTORNEY 'July 15, 1941. M N 2.249.026

AIRPLANE Filed Feb. 28, 1938 6 Sheets-Sheet 2 July 15, 1941, G. H. MOU'RNING. ETAL 2.249.026

AIRPLANE 6 Sheets-Sheet-S Filed Feb. 28, 1938 lNVEN-TORS 4 ATTORNEY AIRPLANE Bywxm 6 Sheets-Shee't 6 Filed Feb. 28, 1938 INVENTORS ATTORNFY and rotative positions.

Patented July 15, 1941 kessing, Louisvilleyli Milton, Louisville, Ky.

y., assignors to John L.

Application February 2a, 1938, saaisal ,1;

8 Claims.

This invention relates toaircraft, and more particularly to a flying machine that ,canbe piloted in the same manner as a. conventional Q airplane, but which is convertible into aircraft of the type having rotative sustaining means,

in which the sustaining means takes the form of a. horizontal wing convertible into a rotor composed of a plurality of sustaining blades or wings actuated by relative air flow.

In addition to facilitating landing, etc., the principal objectof converting a fixed straightflight wing into a rotative sustaining" means, is to provide means for retarding the-fall of such aircraft in the event of failure of motive power,

yet providing, when not so converted, the desirable straight-flight operating qualities of a conventional power-driven gliding airplane, such as speed, maneuverability, emciency in operation, and general all round performance."

Thus, it is the object of this invention to provide a sub-divided horizontal wing, carried by a substantially upright axis structure, that is capable of ready and instant conversion into a multiple-blade sustaining rotor forefiecting' a safe and controlled landing in restricted spaces,

or in emergencies, and which is further capable of ready and instant conversion intoa fixed,-

horizontal-wing providing the required characteristics for conventional straight-flight aircraft; Ther'efora'this invention provides in a single aircraft, the superior advantages of conventional airplane structure for ordinary and normal flying, and in addition the desirable safe landing qualities of the wind-driven sustaining rotor.

The invention furthermore, is specifically concerned with the novel arrangement and construction of the convertible sub-divided wing,

whereby such wing may constitute the primary means of sustention for the aircraft, and also of certain supplemental lifting surfaces'or wings with which the aircraft may be equipped without affecting the dual operating qualities of the coin vertible sub-divided wing.

Another object of the invention resides in the arrangement and mounting of. the sub-divided wing ,so as to minimize, and reduce materially, objectionable forces encountered in both normal A still further object of this invention resides in the arrangement of the sustainingparts of the sub-divided wing so that roughness and -vibrations in the rotor system are reduced materially, thereby minimizing dangers incident to fatigue in such parts.

Another object of this invention resides in the novel construct on and anism ,throughwhic readilya'nd subdivided-wing is o erted froin a sustaining mean having mg-igualities into; .one; hav-. 'ing the qualitiesof-aniriltigilabladerotbrwing, driven or actuatedbylthe relative atmospheric air flow. or vice versa.

A furtherobjectof'my inventionresides in the-novel construction'and 'arrangement'of the aforesaid mechanisrn, whereby the conversion can be readily and substantially instantly pro- H I vided while the aircraft is in flightor landed.

A still furtherobisct of this invention resides in the novel construction and'mountingof the blades forming the sub-divided wing in, such a. manner that theywill, when in" rotor- DOSition, I v

unitarily rotate about a common axis as a result of air flow prcdncedjhythe motion of the-aircraft in termsc-f the-atmosphere, and which will automatically change'pitch, when moved tothe rotor position or restored to fixed-Whig position,

to pr vide the proper wing Ycharacteristics in either positionz'the mounting ofthe bladesbeing such as to permitindependent verticalarticula .f

tion of each blade wherebyeach-.blade"can-be relatively, free to move independently a vertical planaand thereby be'able to as'sume-xvainfluence of Centrifugal,

rious positions under the lift, and other forces.

In addition tothe foregoing, it sh preferably located above the fuselageflof 'thei-ain craft, so as to raise the center of gravity of the aircraft as a whole, when'such Wing-131 881 ato form a multiple blade rotatable sustaininglmeans,

and to prevent any portion of such f -rotating system from fouling on any part of theair'craft, However; the location of the subdivided "wing may be variedlto accommodate specific r'eqiiir'ements, as influencedby the designand' construction of the remaining parts of the aircraft. Anotherlobject of this invention residesin the provision of braking means 'for'retalrding rotation of .the blades of the sub-dividedv wingfjust' prior, to their restoration 'to-vflxed-wing position.

Another'objectiof thisjinvention resides in th'e provision of means that wlllyeffectlvely and definitely lock the blades of the subdivided'wing in fixed-wing position, and in correct relation with respect to the fuselage of theaircraft.

To this end,- this invention provides an 'aircraft having conventional fixed-wing characteristics in normal flight, in which the sustaining wing for normal flight is sub-divided longitudinally into a plurality of blades orwing's each angement of the mechbo 1 in mind that the sub-divided wing structure -is Figure 19 showing nopitch for the blades when in normal flight position, while-Figures 20 l and 21 illustrate changes in pitch as eflected by sustaining rotor, or retaining the rotatable blades in fixed position and cascaded to form a fixed horizontal wing, with means for readily and quickly changing from one to the other at the will of the operator. 7

While each blade is preferably of a symmetrical form, adopting it to efiicient operation either as a conventional airplane fixed wing, or a rotating sustaining propeller, .certain features of this invention are independent of any particular form of the blades or subdivided wing.-

For a better understanding-of the invention, reference is made to the accompanying drawings in which:

Figures 1, 2 and 3 are general views of an airplane embodying the invention;

Figure 4 is a partial plan view of the upper pivot plate in Figure 3, with cover I removed to show.the relation of certain operating cables, when the blades of the sub-divided wing are in the position illustrated by the solid lines of Figure l;

, Figure 5 is a partial sectional view of the lower pivot plate in Figure 3, as viewed from the underside, showing the relation of the main operating cables, when the blades of the sub-divided wing are in the position illustrated by the solid lines of Figure 1;

Figure 6.15 a partialsectional view. as viewed from the under-side of Figure 12, showing the construction of the operating lever ll;

Figure '7 is a partial section along lines 'l'| of Figure 4 showing the construction of a cable lever arm 2|;

Figures 8 and 9 show the construction of the upper and lower main central bearings appearing in Figures 11 and 12"respectively;

- Figure is an enlarged partial elevational view of Figure 2, illustrating the wall of the fuselage partially removed to show the lever 10 that enables the pilot to actuate the sub-divided wing:

Figure 11 is a partial section taken along lines a I il I of Figures 4 or 5, showing the construction and relation of the blade supports carried by plates Ia. and I, when the blades are in the position illustrated by the dot-dash linesof Figure 1;

position of operating lever 40, when the blades are in the position illustrated by the solid lines of Figure 1;

Figure 14 is a partial plan view, as viewed along lines ll-ll of.Figure 13, showing the devices for locking the blades in non-rotating position;

Figures 15, 16 and 17 illustrate modified forms of locking devices illustrated in Figure 14;

Figure ia'illustrates a modification of Figure 13, wherein the central bearing post is shown re-inforced by a yoke;

Figures 19, 20 and 21 are partial diagrammatic changing the distance between pivots 81 and 82;

Figures 22 and 23 are partial diagrammatic sections illustrating the construction of the blade pivots permitting changes in blade pitch;

Figure 24 is a partially enlarged view showing the connection of strut HI to blade 3!);

Figure 25 is a diagrammatic view showing the operative connections of themain operating cables of Figure 5, and the relations thereof when the blades are in the position illustrated by the dot-dash lines of Figure 1;

Figures 26 and 27 illustrate the changing in pitch of blade 3b;

Figures 28 through 32 illustrate a modified arrangement and construction for the sub-divided wing, and the relative mode of operation of the blades.

Referring more in detail to the aforesaid drawings, it will be observed that, in Figures 1, 2 and 3, a conventional low-wing cabin monoplane is equipped with the invention, thereby converting same into an aircraft simulating conventional bi-plane operation, when the additional upper divided-wing is in straight flight conditions. The solid lines of Figure 1, indicate the ascension or conventional normal-flight of the aircraft; this being according to standard conventional airtion, the blades, when forming the sustaining propeller, rotate in the direction indicated by circular arrows I3, as a result of relative air-flow thereover. It is important to observe the particular movement of each blade of the upper divided-wing, while the blades are moving to and from sustaining propeller position. For instance, blades 3a and to move toward each other, when moving to form a wing for conventional straight flight, and, at the end of such movement assume a position substantially parallel one to the other and at ri ht angles to the fuselage of the aircraft. Similarly, blades 3b and 41) function. Thus, in conventional straight-flight condition, the profiles of blades 3a4a and Sb-lb combine to form a profile suitable for conventional straight-flight, havingan efficiency approaching, or practically equaling, the aerodynamic'efiiciency of many of the fixed conventional, unidirectional and unsymmetrical, aerofoil sections.

on the other hand, longitudinally opposed straight-flight blades to and lb move toward sections of the rotatable blades of the sub-divided 5011- Therefore, w n h inclined blades are nected at its apex to sleeve 1b. The upper end of sleeve lb carries a thrust roller-bearing, the particular construction of same being represented in Flg. 8. The lowerend of sleeve lb secured to a bearing cup Ic, which carries a thrust roller-bearing 31, the particular construction "of same being represented in Fig. 9. The outer race of the upper bearing 38 is secured to sleeve lb,

while the inner race of same is secured to the stationary vertical-shaft 28. Similarly, the outer race of the lower bearing is secured-in the Thus, in sustaining propeller position, the

blades rotate simultaneously about a common axis in a clockwise direction; the trailing edge of each blade being higher than the leading or forward edge.

While it is customary to proportion and oonstruct aircraft to provide inherent stability, the invention provides for changes in wing dihedral, of the .upper divided-wing, to obtain proper lateral stability, and thereby compensate for changes in stability that may result when the invention is applied to a conventional monoplaneI It is to be further understood that, while the divided-wing may be readily and easily applied to a conventional low-wing monoplane, this invention also has for its purpose the design of aircraft of various types incorporating the combined functions of the divided wing. For instance, in applying the principles of this invention to a high-wing monoplane, the single wing is divided, and proportioned to provide proper flight characteristics in both conventional straight-flight position and sustaining propeller position. Similarly, the .upperwing of a conventional bi-plane may be so designed.

In Figure 1 there is diagrammatically illustrated a sub-divided wing 3w3b|a4b mounted for permissible rotation about a vertical bearing arranged within the cabin of the air-- craft. A lower wing 2 is also illustrated and pro vided with the necessary ailerons for the aircraft. At the rear end of the fuselage I, a conventional rudder and elevator' assembly is shown; while at the front end of the fuselage, a radial engine 5 and propeller 8 is illustrated.

In Figs. 2 and 3, a cylindrical chamber 9, projecting from the top of the fuselage I, is covered by a lower circular plate 8 of the sub-divided wing assembly. Rigidly attached to the lower plate 8 is an upper circular plate I. Four ver-,

tical, propeller-blade sustaining posts 220., 23d,

24a and 2511 are pivotally mounted between plates 1 and 8, and each post carries a corresponding blade 31:, 4a, 3b and 4b respectively. In Figs. 1 and 3, struts I8, I8a, II and-IIa are illustrated connecting their respective blades 3b,

4b, 4a and 3a. These struts serve normally to reinforce the blades for straight flight. and further serve to control the angle of attack of the blades of the sub-divided wing assembly as-will be described in detail'as the description ad-. vances.

Reference is now'directed to Figs. 11 and 12, which show the general arrangement of the mechanism for actuating the sub-divided wing assembly. It will be observed that the cylindrical chamber 3, projecting upwardly from the fuselage I, terminates within a depending flange of the lower circular plate 8. The central portion of plate 8, via wall members 8a, forms a dome-shaped cylindrical chamber, which is conhearing cup 10, while the inner race of same is secured to the stationary vertical-shaft 28.

The upper end of sleeve 1b is secured to a circular plate la; a circular cover plate I being attached to plate Ia. via screws 89. Each of the plates Ia and 8 are provided with suitable aligning bearings. which pivotally support their respective propeller-blade sustaining posts 22a, 23a, 24a and 25a; between plates Ia and 8. Re-

ferring in particular to sustaining post 24a in a Fig. 11, it will be observed that the upper and lower ends of thesustaining post arereduced in diameter to provide bearingportions 24. It will bev further observed that a lever, 2| is socured to each bearing portion 24, as particularly illustrated in Fig. 7.

Between the junction'of wall members 8a with sleeve 1b, and bearing cup 1c, the sleeve lb is splined providing a reciprocating bearing surface for actuating member 38. Figs. 5, 6 and of member 38 and to distribute the thrust of the 14 each show the splined construction of actuating member 38 and sleeve 'Ib. Referring again to Fig. 11, it will be observed that the actuating member 38 carries a circular plate 48, which, when the member 38 is in its, upper position, embraces rollers' 88 to limit the upward movement rotating wing assembly onto rollers" 68. In Fig.

11 the plate 48 is represented engaging rollers 88, in which condition the sub-divided wing assembly, is actuated to its sustaining propeller I position, as will tail.

Attached to the fuselage I, is a depending circular member- 58, having a central, aperture through which actuating member- 38 passes. Bolts 8| serve to secure the circular member 58 to the fuselage I. On the upper surface of member 58, a circular braking medium 49 issebe hereinafter described in de cured, which serves to retard rotation of the rotating wing assembly, when the actuating member 38 is moved to its lower position. When the actuating/member 38 is in its lower position," the sub-divided wing assembly is actuated to its nor- 'mal or conventional straight-flight position, as

will be hereinafter'described in detail. Fig. 13 shows the relation of circular plate 48, braking medium 49 and actuating member 38, when the latter is in its lower position.

As represented in Figs. 6, 12 and 14, bearing lugs 43-are secured tothe' lower surface of member 58. A lever 48 is pivotally secured to said lugs 43via a bearing pin I. As illustrated in II, which engage bearing su Fi 6, lever 48 is provided with a pair of rollers a pair of annular rings carried by the lower end of actuating member 38. Thus, in the rotating condition of the rotating wing assembly, rollers ll permit actuating member 38 to revolve freely.

Referringin particular to Fig. 12, it will be observed that a pairof cables. 45 and 41 are provided with suitable cable ends 42, which are pivotally secured to lever 48 via pins 46. Thus, a-downward pull on cable 45 lowers the actuating faces 55.-provided by lines.

member 38, while a downward pull on cable 41 raises the actuating member 38.

To facilitate operation of cables 45 and 4.1, a suitable hand operated lever 16 is provided, as illustrated in Fig. 10. To further assist in-the operation of cables 45 and 41,- suitable pulleys 19 and 80 are provided. To retain the hand operated lever 16 in either of its extreme positions, a conventional plunger-operated spring catch is provided. Thus, with the hand operated lever in its forward position, as illustrated, the actuating member 38 is in its lower position. Accordingly, when the hand operated lever 16 'is the reverse position, the actuating member '38 is, in raised position. j

With further reference to Fig. 10, it will be observed that the vertical shaft 26 is reinforced by means of a cross bar 14 anchored to the sides of thejfuselage, and a flange which secures the shaft to a floor 8| within the fuselage.

Having thus far described the relation and 1 construction of the principal actuating parts,

reference is now'directed to Figs. 4, 5, 11 and for an understanding of the manner of operationof the sub-divided wing assembly and associated parts.

Referring in particular to the upper portion of Fig. 11, and Fig. .4, it will be observed that four cables l5, l1, |8 and I9 connect diagonally disposed levers 2|; each cable being provided with a suitable cable end 20 and pin 28. In observing the construction illustrated in Fig. 4, it must be remembered that the parts are shown in their positions assumed when the sub-divided wing assembly is in the conventional or straightflight condition, and that such parts are as would be seen with the cover plate I removed in Fig. 1. To further assist in the understanding of Fig. 4, dot-dash lines radiate from each bearing post 22, 23, 24 and 25, which represent the center'lines of their corresponding sub-divided wing blades. Thus, characters 3a, 4a, 3b and 4b, which correspond with the sub-divided wing blade indentifications, designate the centerlines of the relative blade positions with the levers as shown in heavy Accordingly, it will 'be apparent that, as each lever 2| is moved to its indicated dotted position, each corresponding blade will move through the angle indicated by the letter A. When thus moved to this position, the subdivided wing assembly will assume its sustaining propeller condition. From the foregoing, it is believed obvious that cables I5, l1, l8 and I9 serve primarily as load distribution cables, and do not directly govern operation of the blades of the sub-divided wing assembly. Thus, foran understanding of the relation and operation of the cables serving to govern the operation of the blades of the sub-divided wing assembly, reference is directed to the lower portion of Fig. 11, Fig. 5 and Fig. 25.

the blades of the sub-divided wing assembly are in their sustaining propeller condition, that is, actuating member 38 in its raised position. 7 It is believed that the diagrammatic illustration of the cables in Figure.25 is sufliciently clear to require no further explanation, thus the operation of same will now be outlined Thus, since the actuating member 38 is assumed to be in its upper position, in illustrating the corresponding positions of the levers 2| and operating cables in Figure 25, it will now be assumed that the actuating member 38 is moved to its lower position. Under such condition, lower lugs 10 and upper lugs 33, carried by actuating member 38, move simultaneously downwardly. In so moving, lugs 10 ,exert tension on their associate cables 32--32a and 3|3|a, rotating their corresponding levers 2| toward their conven:-

tional flight position. It is also important to observe that, as lugs 10 exert tension on their associate cables, lugs 33 relieve tension on their associate cables -3011 and 2929a. Thus, a definite rotation of each lever 2| is provided through a degree angular movement. Obviously, actuating member 38 in raising provides a reverse operation of the cables 29-29a, 30--30a, 3|-3|a and 3232a.

Coordinating the showing of Figures 25, 11 and 12 with Fig. 1, it will be observed that the relative positions of the parts shown in Figures 25, 11 and 12 correspond with the dot-dash positions of the sub-divided wing blades in Fig. 1. Similarly, the relative positions of the parts shown in Figures 4, 5, 10 and 13 correspond with the full line positions of the sub-divided wing blades in Figure I. To assist in the understanding of Fig. 5, dot-dash lines, similar to those employed in Fig. 4, radiate from each bearing post '22, 23, 24 and 25, which represent the center lines of their corresponding sub-divided wing blades. Thus, characters 3a, 4a, 3b and 4b, which correspond with the sub-divided wing blade identifications, designate the center lines of the relative blade positions with the levers as shown in heavy lines. Accordingly, as each lever 2| in Figure 5 is rotated to its indicated dotted position, each corresponding blade will move through the angle indicated by the letter A.

In the performance of this invention, it is essential that the sub-divided wing assembly assume a definite position with respect to the fuselage of the craft, when the sub-divided wing assembly is in the conventional or normal flight As hereinbefore described, actuating member 38 is splined to sleeve 1b, and is further'constructed and arranged for reciprocating movement on sleeve 1b. From the figures now under consideration, it will be observed that the circular plate 48 is provided with a pair of dicondition. To'provide for this feature, suitable locking pawls are provided, and arranged as illustrated in Fig. 14. In order to distribute the forces, a plurality of pawls are provided, each disposed on a different radius and adapted to register with a corresponding aperture in the circular plate 48. To further assist in the understanding of the construction and operation of the locking pawls of Figure 14 reference is also directed to Figure 15.

It will be noted that for each pawl a pair of bearing lugs 52a are securedto the lower surface of circular member 50. The pawl member consists of a tapered locking pin 5| carried by a suitable lever 52 which is pivotally secured to the pair of bearing lugs 520. via pin 53. A weight 54 serves to bias locking pin 5| toward the circularplate 48. With the foregoing construction it will be apparent that an automatic locking and unlocking arrangement is provided, and one that will provide definite alignment of the sub-divided wing assembly with the fuselage.

, magnet remains energized. control of the electromagnet 59, a suitable elec- To understand the operation of the locking pawls it will be assumed that the actuating member 38 is raised. Under this condition, circular plate 48 will disengage the brake medium 49 and lift free of the locking pins 5|. When the actuating member 38 is thus raised, the subdivided wing blades assume their sustaining propeller positions and since circular plate 48 is free of the locking pins 5|, the sub-divided Wing assembly is free to rotate as hereinbefore described.

In restoring the sub-divided wing blades to conventional or normal flight conditions, actuating member 39 is moved to its lower position.

In moving to its lower position, circular plate 48 will depress locking pins 5|, by reason of the pivotal construction of lever 52, and engage the braking medium 49 to retard rotation of the subdivided wing assembly. When the circular disc has reduced its speed sufiiciently, and the apertures in circular plate 48 comparatively slowly move into aligning position with their corresponding locking pins 5|, the pins 5| will drop into the apertures, and rigidly lock the subdivided wing assembly in its proper'position. b. viously, as long as the circular plate 48 rotates at a comparatively high speed, the locking pins will not have sufiicient time to drop into their profile form may vary from'point to point along its span. I

Each blade is preferably formed as illustrated in Figs. 19, 20, 21, 26 and 27, and, in the embodiment, the profile form is varied from root to beginningof tip so as to provide a proportional tapering in the thickness of the blade. In this respect attention is directed to Fig. 3.

Referring in particular to Figs. 19, 20 and 21, it will be observed that the angle of attack of .amount of overlap of adjacent blades, for instance, 3b-4b.

As previously mentioned,-the angle of blades 3b and 4b must be reversed when all blades are actuated to their sustaining propeller positions.

This requirement will be obvious upon inspection of Fig. 1, as blades 3b and 4b, in moving to the position indicated by their corresponding dot-- dash lines, must have their angleof attack reversed in order to provide for rotation in the dicorresponding apertures, and will be repeatedly knocked away from the plate 48 until the wing assembly practically ceases rotation.

In Figure 17 a spring-pressed locking pin 62 is illustrated as an alternate arrangement for the locking pawl shown in Figure 15. In Figure 1'7, a cylindrical member 63 is secured to the lower surface of the circular member 50, and serves as a guide for the tapered locking pin 62. A spring 65 serves to bias the pin toward the circular plate 48. Its operation is analogous to that outlined for Figs. 14 and 15.

In Figure 16, the structure illustrated in Fig. 17 is modified and provided with an ele'ctro-magnet 59, which is adapted to be connected to a suitable source of power view wires 60. When so connected the electro-magnet 59 will attract locking pin'iG, and retain same out of the path of the circular plate 48'as long as the electro- To provide selective trical switch is arranged for operation by the pilot of the craft.

In Figure 12, the lever 40 is illustrated as being pivotally secured directly to the lower surface ofthe circular plate 48. In Figure 18 a modified construction is illustrated, which provides a yoke member 56, secured. to the roof of the fuselage having suitable bearing lugs for the pivot pin 44. It is also important to note that rection indicatedby circular arrows l3.

Referring now to Fig. 11, it will be observed that blades 3b and 3a are each secured to their corresponding posts 24a and 22a through the medium of arms 61 and 12, respectively. In this respect, it is to be understood that blades 4a and 4b are similarly mounted; Figs. 2, 3' and 10 indicating such a construction. It is to .be further understood that each arm 61, 12 and 13 etc. has its center line registering with its corresponding dot-dash line radiating from its corresponding post, as illustrated in Figs. 4, 5 and 25. To further exemplify this construction, reference is directed to Figs. 22 and 23, which illustrate the specific construction of arms 61 for blade 3!). Thus, it is to be understood that all blades and associate arms are similarly constructed.

Referring now to Figs. 22 and 23, it will e.

observed that blade 3b is pivotally mounted on arm 61, which is carried by bearing post 24a.

Note also Fig. 11. To absorb the radial thrust of each arm, when the blades are in their rotating, sustaining propeller position, a split collar composed of blocks 93 and 94 is provided for each arm, and secured in position by screws 85.

As stated hereinbefore, each blade is provided attack of its blade. Thus, since the angle of attack of blades 30. and 4a is toremain the same in both normal-flightand sustaining propeller the yoke 66 also serves to anchor the-stationary Post 26 to the fuselage.

As expressed hereinbefore, each blade an, 3b,

.4a, and 4b is preferably of a symmetrical form,

adopting it to efficient operation either as a conventional airplane fixed wing, or a rotating su'staining propeller. Figs: 19, 20, 21, 26 and 27 illustrate a suitable profile form for the blades.- Taking for example blade 3b in Fig. 19, it will be observed that the blade has a profile form substantlally symmetrical about a line perpendicular to the middle of its chord. Concerning the shape found that the blade may be tapered, double trapezoid, or any other suitable form, and may have a uniform profile form throughout, or the of the blade throughout its length, it has been positions, struts II and He are each securedto their corresponding bearing posts 22a and 23a.

Obviously, therefore, the relation of each blade 3a and 4:1. to its bearing post will remain the same in either of its operating positions. However, struts IO and la are each pivotally secured to the upper circular plate la. Thus, the relation of blades 3b and 4b with respect to their corresponding bearing posts 240 and 25a will be different in each of their operating positions. To illustrate this relation, reference is directed to Figs. 26 and 27, and to Fig. 11. "In Figs. 26 and 27 it will be observed that the 'relatively stationary pivotal connection 39, through strut III causes blade 3b to rotate partially about arm 61, when the'blade is moved from its normal flight position iiltutrated in Fig. 26 to its sustaining proangle of attack of blades 3b and 4b in sustaining propeller positionis changed to correspond with that of blades 3a and do, so as to provide for rotation of the sub-divided wing assembly in the direction indicated by circular arrows l3. Ob-

viously, upon restoring blades 3b and 4b to their normal flight positions, their angle of attack will be restored to correspond with that of blades tween the blades and their corresponding struts.

Accordingly, the foregoing description has clearly described the functional and structural relations-of all the parts of the invention, as represented in the particularembodiment of the inv'ention illustrated in Figs. 1 through 2'7, inclusive. Therefore, a summary operation of the embodiment will now be presented.

In normal, or straight-flight conditions, the

' blades of the sub-divided wing assembly assume the position illustrated in Figs. 1, 2 and 3. In this condition, the relation of the blades formin the sub-divided assembly will simulate the operation of a conventional, unidirectional and unsymmetrical, aerofoil section. Thus, the desirable quantities of a conventional power driven gliding airplane, such as speed, maneuverability, efficiency in operation, etc., are retained.

To provide for a ready and instant conversion of the aircraft into one having a multiple-blade sustaining propeller for eflecting a safe and controlled landing in restricted spaces, or in emergencies, mechanism, actuatable through a system of cables via a central lever II, is provided.

Therefore, the operator of the aircraft, by operating lever 16 to its rearward position, automatically releases the brake, release the mechanical aligning lock on the sub-divided wing structure, moves the blades to form a rotative susv taining propeller, and automatically and simultaneously provides a proper angle of attack for each blade, whereby the relative air flow over the sustaining blades will place the sub-divided wing assembly into rotation, as represented by circular arrows l3.

From sustaining-propeller position the operator may restore the blades to their normal flight conditions by merely restoring central lever 18 to its normal position. Obviously, the latter may be accomplished while in flight or landed, according to the will of the operator of the aircraft. Similarly, the operation of the aircraft to a sustaining propeller condition may be effected prior to take-off under which condition the operation of a conventional auto-gyro is simulated.

peller position illustrated in Fig. 27. Thus, the I A very important feature resides in the construction and arrangement of the mechanisms, such as to employ cables and other light-weight constructions affording the maximum strength for the least weight, which is of extreme importance in the design of aircraft,

While the particular embodiment-of the invention, relies entirely on the relative airflow over the blades, and their movement to sustaining propeller position, to initiate the rotation of the sub-divided wing assembly, it is to be understood that the construction of the embodiment is such that a mechanical or electrical initiating device may be incorporated to facilitate initial rotation of the sub-divided wing assembly..

--Figs. 28 through 32 inclusive, illustrate a modified embodiment of the invention, so that it will be obvious to those skilled in the'art the various forms the invention may assume. Thus, having made a clear exposition of the functional and structural characteristics of the invention illustrated in Figs. 1 through 2'7 inclusive, only the salient. features illustrated in Figs. 28 through 32 relatively, diagonally opposed blades 81 and ML are stationary while blades 88 and 89 move through their 90 degree path. Fig. 30 illustrates the relation of the blades in their sustaining propeller position.

In Figs. 28, 29 and 30, the blades of the subdivided wing assembly are illustrated as having a triangular shape. In Fig, 32 the blades are arranged to provide 'a conventional aerofoil shape. Thus, with the thorough exposition of the construction of the former embodiment embraced by Figs. 1 through 27, it is believed the structural modifications embraced by Figs. 28 through 32 will be manifest to those skilled in the art, and that their teachings are adequately sufflcient to permit a complete practicing of same in accordance with the spirit and intent of this disclosure.

Having thus described the invention, we claim:

1. A- device for use with a. heavier than air machine comprising, a support rotatably mounted upon the fuselage of the said machine; four blades each pivotally secured to the said support for a lateral movement in the same plane; means operatively connected to each of the said blades for moving them into a' position substantially In restoring from sustaining propeller to normal flight conditions, lever 18 is pushed forwardoperation is foolproof, and requires a minimum of attention by the operator, which is of extreme importance in the case of emergencies.

at right angles one with the other to form an aerodynamically-driven rotating wing system, and for folding the blades in pairs into longitudinal alignment one with the other to form a substantially uniform longitudinal wing structure; means operatively associated with the said support for retaining the said rotatable support stationary so that the folded blades project sub*- stantially longitudinallyoutwardly and beyond opposite sides of the said fuselage; and means releasing the said retaining means when the blades are moved to form the said rotating wing aaeaoae V Y x 7 2. A device for use with a heavier than air machine comprising, a support rotatably mounted above'the fuselage of the machine for rotation substantially in a horizontal plane; four blades each pivotally secured to the said support for lateral movement in the plane of rotation there of; means operatively associated with each of the said blades for moving them laterally into open positions substantially at right angles one with the other to form a wind-driven sustaining propeller, and for moving the blades laterally into folded pairs longitudinally in alignment one with the other to form a horizontal wing structure simulating the operation of a conventional fixed gliding wing; means operatively associated with the said support for retaining the same relatively stationary with the folded blades extending substantially longitudinally outwardly and beyond opposite sides of the fuselage; and means for releasing the said retaining means, when the blades are moved to form the said wind-driven sustaining-propeller.

3. A device for use with a heavier than air machine comprising, a support pivotally mounted upon the fuselage of the machine for rotation in substantially a horizontal plane; four blades each pivotally secured to the said support for lateral movement in the plane of rotation thereof; means operatively associated with each ofv the said blades for moving them laterally about their respective pivotal axis into open positions points clockwise about their respective pivotal axis and simultaneously therewith moving the blades secured at the two remaining diametrically opposed points anti-clockwise about their respective pivotal axis into open positionssubstantially at right angles one with the other to form a wind-driven sustaining propeller; means operatively associated with each of the said blades I for moving the blades-of the first mentioned two diametrically opposed points anti-clockwise about their respective pivotal axis and simultaneously therewithmoving the blades of the said two remaining diametrically opposed points clockwise about their respective pivotal axis into folded pairs longitudinally in alignment one with the other to form ahorizontal wing structure simulating-the operation of a conventional fixed gliding wing; and means operatively associated with the said, blades for retaining the same relatively stationary in their respective folded positions withthe folded blades extending longitudinally outwardly and beyond opposite sides of the said fuselage. I

6. A device for use with '.a, heavier than air machine comprising a support pivotally mounted upon the, fuselage of the machine for rotation in substantially a horizontal plane; a plurality substantially at right angles one withthe other 1 to form a wind-driven sustaining-propeller; and means operatively associated with each of the said blades for moving them laterally about their respective pivotal axis into closed positions of folded pairs longitudinally in alignment one with the other to form a horizontal wing structure simulating the operation of a conventional fixed 9 gliding wing.

4. A device for use with a heavier than air machine comprising, four blades pivotally mounted upon the fuselage of 'the machine for rotation in substantially a horizontal plane as a wind-driven sustaining propeller, each blade having an individual pivotal connection for. lateral ,movement, in the plane of rotation of the said propeller, into relatively closedpositions to form a horizontal wing structure simulating the operation of a conventional fixed gliding wing;

meansoperatively associated with each of the' said blades for moving them laterally about their of blades arranged in groups of two each and having'the blades of 'eachgroup individually v pivotally secured to the said support at diametrically opposedpoints thereof for movement laterally inlthe plane of I rotation of the said support; means'operativelyassociated with each spective pivotal axis into open positions longitudinally in alignment'fone with the other to form a. wind-driven sustaining-propeller; means of the said bladesfor simultaneously moving the blades of each group: laterally about their reoperatively' associated with each of the said blades for simultaneously, moving the blades of each group laterally about their respective pivotal axis into closed positions to form ahorizontal wing structure; and means operatively assorespective individual pivotal connections into closed positions of folded pairs longitudinally in alignment one with the other to form the said horizontal wing structure; means operatively associated with the said blades for retaining the "san'ie relatively stationary in their closed posidiametrically opposed points thereof for movement laterally in the plane of rotation of the said support; means operatively associated with each of the said blades for moving the blades secured at two of the said diametrically opposed 'ciated' with the said" blades for retaining the 45 folded positions, with :the'blades extending longitudinally outwardly and beyond opposite sides of the said fuselage.

same relatively stationary in" their respective 7. A device, fortuse lwith ajheavier than air machine comprising; a;- wind-driven sustainingpropeller consisting-nof four blades disposed at right angles one. tohthe other and pivotally mounted upon the fuselage of themachine for rotation in substantially. a horizontal plane;

means operatively associated with the said blades for folding the same'into pairs extending outwardly from opposite sides'of the said fuselage withthe forward edge ofv the rear blade of each pair abutting the trailing edge of the-corresponding forward bladevto form a' horizontal wing structure simulating I-the operation of a. fixed gliding wing; and means operatively associated with the said blades for moving the same out of their respective folded positions into relative open positions substantially at right angles one to the other to form the said wind-driven sustaining propeller.

8. A device for use with a heavier than air machine comprising, a support rotatably mount-c ed upon the fuselage of the said machine for rotation substantially in a horizontal plane;- four blades each pivotally secured to the said support for lateral movement substantially in the plane of rotation thereof; means operatively associated with each of the said blades for movwing structure simulating the operation of a fixed gliding wing and means operatively associated with the said blades for moving them laterally out of their respective folded positions into relative open positions substantially at right angles one'to the other to form the said winddriven sustaining propeller.

GARLAND H. MOURNING. FRANK H. RICHTERKESSING. 

